Nozzle for combustion-gas turbines



M. sEDLMl-:IR

NOZZLE FOR COMBUSTION GAS TURBINES' Filed March 29, 192'? 2 Sheets-Sheet l T Nm IQ sw l SQ O O /l/l O O Q INVENTOH /MfL SEDLME/R MMA A TTRNE YS M. SEDLMEI'R ocr. A14?, 1930.

NOZZLE FOR COMBUSTION GAS TURBINES Filed March 29, 1927 2 Sheets-Sheet 2 wir/VE@ I l/tI VEN TUR /W/c/MEL 55M 1f/f? BY pk' ATTORNEYS Patented Oct. 14, 1930 IUMH-:2D STATI- 2s ,PATENT- OFFICE MICHAEL SEDLMEIR, F MULH'EIM-BUHBJGEBHANY, ABSIGNOB T0 HOLZWABTH GAS TURBINE C0., 0F SAN FRANCISCO, CALIFORNIA, A CORPORATION OF DELAWABE NOZZLE FOR COIBUSTION-GAS TUBBIN'ES Application. lerl March 29, 1927. Serial No. 179,241,

My present invention relates to nozzles for combustion gas turbines, and has for its object to construct nozzles of this type in such a manner as to obtain a sturdy and durable articlel and to facilitate the manufacture, finishing, cleaning, and cooling of I the nozzle.

A preferred and satisfactory embodiment of my invention is illustrated by the accompanying drawings, in which Fig. 1 is a lon 'tudinal section of the im roved nozzle, with an indication of the adjacent parts of 'the' apparatus; Fig. 2 is a face view, looking in the direction of the arrow 2 in Fig. 1; Figs. 3, 4 and 5 are sections on lines 3-3, 4 4, and 5-5. respectively of Fig. 1;

and Fig. 6 shows a modification of the noz.

zle outlet shown in'Fig. 2.

In Fig. 1 I have indicated-diagrammatically certain parts of a turbineof the Holzwarth type, viz.: 'a combustion chamber 10 from which combustion gases under` pressure pass through an outlet controlled by a-valve 11.,into a conduit 12 which delivers such gases into the tapering inlet portion 13 of my improved nozzle13. The outlet ofA this nozzle is adjacent td the path'of blades 14 carried by therotor-15, the axis of which would be a horizontalline in a view such Ias Fig. 1. It will be understood that while I have shown my improved nozzle inconljunction with parts of the type indicated at 10, 11, 12, 14, 15, and while my invention -has been devised primarily for use in conjunction with a turbiner and combustion chamber construction of this type, I do not shown at 22'L in Fig. 6. At the lower portion of the outlet, a sharp edge 23 has been rowish to restrict myself thereto.

'From its narrowest portion or throat13" the passage of the nozzle 13 flares toward its outlet. The body of the nozzle, in which said assage is formed,is cast in one piece of v onel metal or other suitable material able to perform its functions satisfactorily at the high temperatures to which the noz# zle is exposed. Monel metal also has the advantage that it is not oxidizable, and is readily worked, polished, and welded The jacket for the water or other medium employedfor cooling the nozzle is formed partly by outer walls such ae 13* and 13" cast integral with the Anozzle bod at the inlet and outlet ends thereof, an artly by a shell 16' made of pieces of MoneFsheet metal welded. to the said walls 13", 13". This construction provides an easily made casting and (before applying the shell .16) the inner walls ofthe jacket can be `cleaned thoroughly,'thus insuring a prolper contact of the water, oil or other coo 'ng medium, vwith such walls.

The cooling medium enters through an opening 17 near the outlet of the nozzle, then passes through a jacket chamber 18 the upper boundary of which is formed by an external surrounding rib 19 on the nozzle bod and then through an aperture 19 in sald rib into an annular chamber 18 lying between the rib 19 and a similar rib 20 nearer to the nozzle inlet. At a point preferably diametrically opposite to thev aperture 19', the rib 20 has an opening 20 through which the cooling medium enters a third jacket chamber, 18, adjacent to the throat of the nozzle. From this chamber the cooling medium passes out through an opening 21.

I have found that in practice, in order to secure the best results, no point of the surface with which the combustion gases come in contact should be farther away than about two inches from the nearest point of the surface with which the cooling medium is in contact. For this reason the tip of the nozzle has been notched or cut olf, as indimade with a straight vertlcal edge or line,

or a curve or arc shape might be adopted as cured in position and the entire nozzle fastened to the conduit 12 in any suitable manner.

As shown in Fig. 2, the longitudinal axis of the main portion of the nozzle is tangential at the part 22 of the nozzle outlet to the median circle indicating the center of the arcuate nozzle outlet. The center of curvature of this nozzle outlet is upon the axis of 'the turbine rotor, which latter has not been illustrated in this case.

Various changes in the specilic form shown' and described may be made within the scope spirit of my invention.

For instance the shell need not beof the 'of the claims Without departing from the same material as the' nozzle body, but can be made from copper being applied to the nozzle body by electrocoppering the nozzle body.` While electroplating, the .jacket should be illed with a suitable material like wax, which is molten and removed, when the thickness' of the electrocopper shell is sufficiently strong.

e I claim:

1. A nozzle for conducting combustion gases" under pressure to the rotor of .a-turbine, comprising a body having an` inlet liange whose surface is perpendicular to the axis of the turbine, said body including a section Whose axis is substantially parallel to the axis of the turbine and which terminates in a constricted portion, and a second section whose axis is. inclined to the axis of bine, comprising a body vhaving an inlet' flange whose surface is perpendicular to the am's of the turbine, said body including a secinversas said ribs whereby a-jacket having a plurality f passages is formed. 1'-

3. A nozzle for conducting combustion gases under pressure to the' rotor of a turbine, comprising a body having an inlet section terminating in a constricte'd portion, and a second section whose axis is oblique to that of said inlet section, said second section -increasing in cross-sectional area from said constricte'd portion toward the discharge end of the nozzle, said body being double walled at both its inlet and discharge ends and single Walled at the middle thereof, and a separate shell surrounding the nozzle \body at said single-walled middle portion and connesting the outer walls of said double-walled portions. A

4. A nozzle for conducting combustion gases to the rotor of a turbine,comprising a body having an inlet section and an outlet section, the axis of said outlet section being inclined to the axis of said inlet section, said body being'of constricted cross-section intermediate its ends and increasing in cross-sec tional area from such constriction toward the outlet end o f the nozzle, saidbody beingv double-walled over portions thereof adjoining its inlet and outlet ends and 'single- Walled intermediate Vsuch double-Walledpori tions, and a separate shell'surrounding the nozzlebody at said single-Walled intermediate portion and connecting the outer Walls ofsaid'double-walled portions.

In testimony whereof I have my hand.

hereunto set l r MICHAEL SEDLMEIR! tion Whose ams is substantially parallel to the am's of the turbine and which terminates in a constricted portion, and a second section whose axis is inclined to the axis oi' the turbine and' increasing in cross-sectional area from said consnicted portion to the dis` charge end of said nozzle, said body being double-walled at both its inlet and discharge ends and singlewalled at the middle thereof, and a separate shell surroundingthe nozzle body at said single-walled middle portion thereor` and connecting the outer walls of said double-walled portions, said body being provided with external ribs at said single-Walled middle portion and said shell surrounding said nozzle body in contact with 

